Radial positioning, torque transmitting and locking structure for turbine side rotor of liquid rocket engine

Abstract

The invention discloses a radial positioning, torque transmitting and locking structure for a turbine side rotor of a liquid-propellant rocket engine, and relates to the technical field of liquid-propellant rocket engines. The radial positioning, torque transmitting and locking structure for the turbine side rotor of the liquid rocket engine comprises a turbine disc, a main shaft, a lining and a shaft end nut. According to the turbine side rotor structure, torque is transmitted through a flat key or a rectangular spline or an involute spline, the two sides of the turbine disc are located in the radial direction, a shaft end nut and a main shaft are screwed and screwed in place to load torque, a flange of the shaft end nut is riveted in a punching point mode and embedded into a groove of the turbine disc, and axial locating and locking of the turbine disc and a lining are achieved. According to the radial positioning, torque transmitting and locking structure for the turbine side rotor of the liquid rocket engine, turbine disc double-side positioning is adopted, the radial positioning precision of the turbine rotor is effectively improved, the machining procedure is simplified, the interchangeability and universality of the turbine rotor are enhanced, the production and assembly efficiency is remarkably improved, and the operation reliability of the turbine side rotor is improved.

Description

Technical Field

[0001] This invention relates to the field of liquid rocket engine technology, and in particular to a radial positioning, torque transmission and locking structure for a turbine-side rotor of a liquid rocket engine. Background Technology

[0002] The turbopump is one of the core components of a pump-fed liquid rocket engine, serving as its "power heart." The structural layout, assembly precision, and operational reliability of the turbopump rotor system directly determine the engine's thrust stability, efficiency, and service life. The turbine rotor operates under particularly harsh conditions within the rotor system, requiring stable operation at high speeds, high temperatures, and high loads. Therefore, stringent requirements are placed on the turbine rotor's positioning accuracy, torque transmission method, locking structure, and assembly processability.

[0003] At present, the turbine-side rotors of turbopumps for liquid rocket engines in service and under development both domestically and internationally generally adopt single-sided radial positioning of the turbine disk and main shaft, torque transmission by pins, axial bolt connection, and spot welding locking. This has problems such as poor single-sided positioning accuracy, cumbersome processing procedures, and poor interchangeability between different turbine rotors. Summary of the Invention

[0004] The purpose of this invention is to overcome the shortcomings of the prior art and provide a radial positioning, torque transmission and locking structure for the turbine-side rotor of a liquid rocket engine, which further improves the radial positioning accuracy, simplifies the processing steps, optimizes the locking structure, and improves the interchangeability of turbine rotor parts, thereby improving the operational reliability of the turbine-side rotor.

[0005] The technical solution adopted by this invention to solve its technical problem is as follows:

[0006] A radial positioning, torque transmission and locking structure for a turbine-side rotor of a liquid rocket engine includes a turbine disk, a main shaft, a bushing, and a shaft end nut.

[0007] The turbine disk has two radial positioning surfaces: a first radial positioning surface and a second radial positioning surface. The main shaft also has two radial positioning surfaces: a first radial positioning surface and a second radial positioning surface. The first radial positioning surface of the turbine disk is in direct contact with the first radial positioning surface of the main shaft, while the second radial positioning surface of the turbine disk is indirect contact with the second radial positioning surface of the main shaft via the bushing.

[0008] The turbine-side rotor structure is equipped with a flat key, rectangular spline, or involute spline for transmitting torque.

[0009] The turbine disk and the bushing are axially positioned and locked by the shaft end nut.

[0010] Preferably, the turbine disk and the main shaft, the turbine disk and the bushing, and the bushing and the main shaft are all radially fitted with clearance.

[0011] Preferably, the turbine disk is provided with an outer end face, the shaft end nut is provided with an inner end face, and an axial clearance is provided between the outer end face of the turbine disk and the inner end face of the shaft end nut.

[0012] Preferably, the turbine disk has two or more turbine disk grooves for locking.

[0013] Preferably, the main shaft is provided with one main shaft thread, and the shaft end nut is provided with one shaft end nut thread. The main shaft thread and the shaft end nut thread are screwed together and tightened to a specified position for axial fixation of the turbine disk and the bushing.

[0014] Preferably, the shaft end nut is provided with a shaft end nut retainer, which is used to punch and rivet the shaft end nut retainer after the turbine disk, main shaft, and bushing are assembled in place, so that the shaft end nut retainer is partially deformed and embedded in the groove of the turbine disk, thereby realizing the axial positioning and locking of the turbine disk and the bushing.

[0015] Preferably, the thickness of the flange of the shaft end nut is 0.3-2mm.

[0016] Preferably, the shaft end nut is provided with two or more shaft end nut grooves, which serve as process grooves for the thread loading torque of the shaft end nut.

[0017] Preferably, the bushing is made of copper alloy material.

[0018] Compared with the prior art, the present invention has the following advantages:

[0019] (1) The liquid rocket engine turbine-side rotor radial positioning, torque transmission and locking structure of the present invention has two radial positioning sections on the turbine disk, which realizes the dual-side positioning of the turbine disk and improves the radial positioning accuracy and operational reliability of the turbine rotor.

[0020] (2) In the radial positioning, torque transmission and locking structure of the liquid rocket engine turbine-side rotor of the present invention, the flat key, rectangular spline or involute spline of the turbine disk and the main shaft are pre-machined and do not require matching machining. After the turbine-side rotor is assembled in place, the shaft end nut retaining edge punch is riveted to the turbine disk groove to achieve locking, which simplifies the machining process, optimizes the locking structure, enhances the interchangeability and versatility of the turbine rotor, and improves production and assembly efficiency. Attached Figure Description

[0021] To more clearly illustrate the technical solutions of the embodiments of this invention, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of the installation of a radial positioning, torsion transmission and locking structure for a liquid rocket engine turbine-side rotor according to an embodiment of the present invention;

[0023] Figure 2 This is a schematic diagram of the turbine disk structure in an embodiment of the present invention;

[0024] Figure 3 This is a schematic diagram of the main shaft structure in an embodiment of the present invention;

[0025] Figure 4 This is a schematic diagram of the structure of the shaft end nut in an embodiment of the present invention;

[0026] Explanation of the markings in the image:

[0027] 1-Turbine disk; 2-Main shaft; 3-Bushing; 4-Shaft end nut; 11-Turbine disk first radial positioning surface; 12-Turbine disk second radial positioning surface; 13-Turbine disk outer end face; 14-Turbine disk groove; 21-Main shaft first radial positioning surface; 22-Main shaft second radial positioning surface; 23-Main shaft thread; 41-Shaft end nut thread; 42-Shaft end nut flange; 43-Shaft end nut groove; 44-Shaft end nut inner end face. Detailed Implementation

[0028] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0029] It should also be understood that the terminology used in this specification is for the purpose of describing particular embodiments only and is not intended to limit the invention. As used in this specification and the appended claims, the singular forms “a,” “an,” and “the” are intended to include the plural forms unless the context clearly indicates otherwise.

[0030] It should also be further understood that the term "and / or" as used in this specification and the appended claims refers to any combination of one or more of the associated listed items and all possible combinations, and includes such combinations.

[0031] Example

[0032] See Figure 1 The liquid rocket engine turbine-side rotor radial positioning, torque transmission and locking structure shown includes turbine disk 1, main shaft 2, bushing 3, and shaft end nut 4.

[0033] See Figure 2 The turbine disk 1 shown has two radial positioning surfaces: a first radial positioning surface 11 and a second radial positioning surface 12. (See reference...) Figure 3 The spindle 2 shown has two radial positioning surfaces: a first radial positioning surface 21 and a second radial positioning surface 22. The first radial positioning surface 11 of the turbine disk is in direct contact with the first radial positioning surface 21 of the spindle, and the second radial positioning surface 12 of the turbine disk is in indirect contact with the second radial positioning surface 22 of the spindle through a bushing 3.

[0034] The turbine-side rotor structure is equipped with a flat key, rectangular spline, or involute spline for transmitting torque.

[0035] The turbine disk 1 and the bushing 3 are axially positioned and locked by the shaft end nut 4.

[0036] The turbine disk 1 and the main shaft 2, the turbine disk 1 and the bushing 3, and the bushing 3 and the main shaft 2 are all radially fitted with clearance.

[0037] The turbine disk 1 is provided with an outer end face 13, and the shaft end nut 4 is provided with an inner end face 44. An axial clearance is provided between the outer end face 13 of the turbine disk and the inner end face 44 of the shaft end nut.

[0038] The turbine disk 1 has 4 turbine disk grooves 14 for locking.

[0039] Spindle 2 has one spindle thread 23, see reference. Figure 4 The shaft end nut 4 shown is provided with a shaft end nut thread 41. The main shaft thread 23 engages with the shaft end nut thread 41 and is tightened to the specified position for axial fixation of the turbine disk 1 and the bushing 3.

[0040] The shaft end nut 4 is provided with a shaft end nut retainer 42, which is used to punch and rivet the shaft end nut retainer 42 after the turbine disk 1, main shaft 2, and bushing 3 are assembled in place. This causes the shaft end nut retainer 42 to be partially deformed and embedded in the turbine disk groove 14, thereby achieving axial positioning and locking of the turbine disk 1 and the bushing 3.

[0041] The thickness of the flange of the shaft end nut is 0.3-2mm.

[0042] The shaft end nut 4 is provided with 4 shaft end nut grooves 43, which serve as process grooves for loading torque on the shaft end nut thread 41.

[0043] Bushing 3 is made of copper alloy.

[0044] The function of the radial positioning, torsion transmission, and locking structure of the turbine-side rotor of this liquid rocket engine is as follows:

[0045] The turbine disk's first radial positioning surface 11 and the main shaft's first radial positioning surface 21 are in direct contact, achieving the first radial positioning of the turbine rotor. The turbine disk's second radial positioning surface 12 is indirectly in contact with the main shaft's second radial positioning surface 22 through the bushing 3, achieving the second radial positioning of the turbine rotor. When the liquid rocket engine is working, the high-temperature gas drives the turbine disk 1 to rotate at high speed, transmitting torque to the main shaft 2 through a flat key, rectangular spline, or involute spline, causing the main shaft 2 to rotate synchronously at high speed. After the turbine disk 1, main shaft 2, and bushing 3 are assembled in place, the shaft end nut thread 41 is screwed into the main shaft thread 23 and tightened to the specified position. Tightening torque is applied through the shaft end nut groove 43, and then the shaft end nut flange 42 is riveted to a point, causing the shaft end nut flange 42 to deform locally and embed into the turbine disk groove 14, thereby ensuring the precise axial positioning and reliable locking of the turbine disk 1 during the operation of the liquid rocket engine.

[0046] The radial positioning, torsion transmission and locking structure of the liquid rocket engine turbine-side rotor of the present invention adopts turbine disk double-sided positioning, which effectively improves the radial positioning accuracy of the turbine rotor, simplifies the processing procedure, and ensures a stable and reliable locking structure; at the same time, it enhances the interchangeability and versatility of the turbine rotor, significantly improves production and assembly efficiency, and improves the operational reliability of the turbine-side rotor, making it widely applicable in the field of rocket engines.

[0047] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in the present invention, and these modifications or substitutions should all be covered within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

[0048] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A radial positioning, torsion transmission, and locking structure for a turbine-side rotor of a liquid rocket engine, characterized in that... It includes a turbine disk (1), a main shaft (2), a bushing (3), and a shaft end nut (4); The turbine disk (1) is provided with two radial positioning surfaces, namely the first radial positioning surface (11) and the second radial positioning surface (12); the main shaft (2) is provided with two radial positioning surfaces, namely the first radial positioning surface (21) and the second radial positioning surface (22); the first radial positioning surface (11) of the turbine disk is in direct contact with the first radial positioning surface (21) of the main shaft, and the second radial positioning surface (12) of the turbine disk is indirectly in contact with the second radial positioning surface (22) of the main shaft through the bushing (3); The turbine-side rotor structure is equipped with a flat key, rectangular spline, or involute spline for transmitting torque; The turbine disk (1) and bushing (3) are axially positioned and locked by the shaft end nut (4).

2. The radial positioning, torque transmission, and locking structure for the turbine-side rotor of a liquid rocket engine according to claim 1, characterized in that, The turbine disk (1) and the main shaft (2), the turbine disk (2) and the bushing (3), and the bushing (3) and the main shaft (2) are all radially fitted with clearance.

3. The radial positioning, torque transmission, and locking structure for the turbine-side rotor of a liquid rocket engine according to claim 1, characterized in that, The turbine disk (1) is provided with an outer end face (13), and the shaft end nut (4) is provided with an inner end face (44). An axial gap is provided between the outer end face (13) of the turbine disk and the inner end face (44) of the shaft end nut.

4. The radial positioning, torque transmission, and locking structure for the turbine-side rotor of a liquid rocket engine according to claim 1, characterized in that, The turbine disk (1) is provided with two or more turbine disk grooves (14) for locking.

5. The radial positioning, torque transmission, and locking structure for the turbine-side rotor of a liquid rocket engine according to claim 1, characterized in that, The main shaft (2) is provided with a main shaft thread (23), and the shaft end nut (4) is provided with a shaft end nut thread (41). The main shaft thread (23) and the shaft end nut thread (41) are screwed together and tightened to a specified position for axial fixation of the turbine disk (1) and the bushing (3).

6. The radial positioning, torsion transmission and locking structure for the turbine-side rotor of a liquid rocket engine according to claim 1, characterized in that, The shaft end nut (4) is provided with a shaft end nut retainer (42), which is used to punch and rivet the shaft end nut retainer (42) after the turbine disk (1), main shaft (2) and bushing (3) are assembled in place, so that the shaft end nut retainer (42) is partially deformed and embedded in the turbine disk groove (14), thereby realizing the axial positioning and locking of the turbine disk (1) and bushing (3).

7. The radial positioning, torsion transmission and locking structure for the turbine-side rotor of a liquid rocket engine according to claim 6, characterized in that, The thickness of the end nut retainer (42) is 0.3-2mm.

8. The radial positioning, torque transmission and locking structure for the turbine-side rotor of a liquid rocket engine according to claim 1, characterized in that, The shaft end nut (4) is provided with two or more shaft end nut grooves (43) as process grooves for loading torque of the shaft end nut thread (41).

9. The radial positioning, torsion transmission and locking structure for the turbine-side rotor of a liquid rocket engine according to claim 1, characterized in that, The bushing (3) is made of copper alloy.

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